GAS TURBINE COMPONENT, INTERMEDIATE STRUCTURE OF GAS TURBINE COMPONENT, GAS TURBINE, METHOD OF MANUFACTURING GAS TURBINE COMPONENT, AND METHOD OF REPAIRING GAS TURBINE COMPONENT

摘要

This gas turbine component comprises a metal intermediate structure (110) and a ceramic layer (130). A gas path surface (102) which faces toward a combustion gas flow path (GP) side in a radial direction (Dr), and a pair of side surfaces (103) which oppose one another in a circumferential direction Dc are formed in the intermediate structure (110). The ceramic layer (130) is formed on the gas path surface (102) of the intermediate structure (110). However, the ceramic layer (130) is not formed on a rotationally upstream corner portion (115u) between the rotationally upstream side surface (103u), on the upstream side in the direction of rotation of a rotor, from among the pair of side surfaces (103), and the gas path surface (102).